EP3093442B1 - Positionnement d'entretoise d'aube et systèmes de fixation - Google Patents

Positionnement d'entretoise d'aube et systèmes de fixation Download PDF

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Publication number
EP3093442B1
EP3093442B1 EP16160455.8A EP16160455A EP3093442B1 EP 3093442 B1 EP3093442 B1 EP 3093442B1 EP 16160455 A EP16160455 A EP 16160455A EP 3093442 B1 EP3093442 B1 EP 3093442B1
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EP
European Patent Office
Prior art keywords
strut
flap
mount
cylinder
bushing
Prior art date
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Active
Application number
EP16160455.8A
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German (de)
English (en)
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EP3093442A1 (fr
Inventor
Enzo Dibenedetto
Matthew E. Bintz
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RTX Corp
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United Technologies Corp
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Publication of EP3093442A1 publication Critical patent/EP3093442A1/fr
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Publication of EP3093442B1 publication Critical patent/EP3093442B1/fr
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/323—Application in turbines in gas turbines for aircraft propulsion, e.g. jet engines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods

Definitions

  • the present disclosure relates to turbomachine vanes, more specifically to mounting systems for vane struts.
  • a plurality of variable vanes having a strut-flap design can be utilized to properly direct air flow to downstream airfoils which can enhance performance.
  • the gap between the upstream strut and the downstream flap of each vane typically needs to be very small to prevent unacceptable leakage from the high pressure side to the low pressure side thereof. This can be achieved by individual custom fabrication having very low tolerances, but such solutions are not proven cost effective in a production environment.
  • EP 1340894 A2 discloses an assembly for a gas turbine engine, comprising struts and pivoting flaps downstream of the struts.
  • US 2012/0163960 A1 discloses a variable vane system for a gas turbine engine.
  • US 3990810 discloses a vane assembly comprising manually adjustable variable vanes.
  • GB 774501 discloses a variable turbine stator blade assembly, each blade comprising a fixed part and a pivotable part.
  • FR 2908828 A1 discloses a deformable seal for variable vanes.
  • a vane strut for a strut-flap vane comprising: an airfoil portion; and a strut mount extending in a radially outward direction from the airfoil portion; characterised in that the strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof.
  • a strut-flap vane system for a turbomachine comprising: a vane strut according to the first aspect; and an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder, wherein the strut cylinder defines a cylinder opening, wherein the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the aft mount portion.
  • a flap mount assembly may be disposed within the cylinder opening, the flap mount assembly including a flap post extending from a flap and rotatable relative to the strut cylinder to allow the flap to change position relative to the vane
  • the flap mount assembly may include a bushing disposed around the flap post, the bushing including threading on an outer diameter thereof.
  • the bushing may include a bushing flange disposed radially inward of the strut cylinder.
  • a flap spanner nut may be meshed with the threading on the bushing to secure the bushing and the flap in a position relative to the strut while allowing the flap post to rotate.
  • the flap spanner nut may be sized to fit at least partially within the cylinder opening and engage with a cylinder flange extending from the strut cylinder.
  • the flap spanner nut may include anti-rotation serrations on a surface thereof that contact the cylinder flange to prevent rotation of the spanner nut after compressing against the cylinder flange.
  • the strut spanner nut may be configured to mount the strut-flap vane to a turbomachine housing.
  • the strut spanner nut may include anti-rotation serrations on a surface thereof that contact the turbomachine housing.
  • an aft mount portion may be removably attached to the strut mount and may define a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder, wherein the strut cylinder defines a cylinder opening, wherein the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the aft mount portion.
  • a method comprising: assembling a flap mount assembly; placing the flap mount assembly proximate to a strut mount of a vane strut, wherein the strut mount extends in a radially outward direction from an airfoil portion of the vane strut, and wherein the strut mount forms a hollow semi-cylinder; and disposing an aft mount portion around the flap mount assembly such that the aft mount portion and the strut mount form a strut cylinder with threading on an outer diameter thereof.
  • assembling the flap mount assembly may include disposing a bushing around a flap post of a flap such that the flap post is attached to the bushing but rotatable relative to the bushing.
  • the method may further comprise disposing a washer between a portion of the bushing and a portion of the flap.
  • the method may further comprise securing the flap mount assembly to the strut cylinder by threading a flap spanner nut around the bushing and tightening the flap spanner nut into a flange of the strut cylinder.
  • the method may further comprise placing the strut cylinder within a turbomachine housing.
  • the method may further comprise securing the strut cylinder to the turbomachine housing by threading a strut spanner nut around the strut cylinder and tightening the strut spanner nut into the turbomachine housing.
  • the flap mount assembly may be secured to the strut cylinder before the strut cylinder is secured to the turbomachine housing.
  • a strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion.
  • the strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof
  • the system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder.
  • the strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion.
  • the flap mount assembly may additionally and/or alternatively be disposed within the cylinder opening and can have a flap post extending from a flap and rotatable relative to the strut cylinder to allow the flap to change position relative to the vane strut.
  • the flap mount assembly may additionally and/or alternatively include a bushing disposed around the flap post, the bushing including threading on an outer diameter thereof.
  • the bushing may additionally and/or alternatively include a bushing flange disposed radially inward of the strut cylinder.
  • the system may additionally and/or alternatively include a flap spanner nut meshed with the threading on the bushing to secure the bushing and the flap in a position relative to the strut while allowing the flap post to rotate.
  • the flap spanner nut may additionally and/or alternatively be sized to fit at least partially within the cylinder opening and engage with a cylinder flange extending from the strut cylinder.
  • the flap spanner nut may additionally and/or alternatively include anti-rotation serrations on a surface thereof that contacts the cylinder flange to prevent rotation of the spanner nut after compressing against the cylinder flange.
  • system may additionally and/or alternatively include a strut spanner nut configured to mount the strut-flap vane to a turbomachine housing.
  • the strut spanner nut may additionally and/or alternatively include anti-rotation serrations on a surface thereof that contacts the turbomachine housing.
  • a vane strut for a strut-flap vane can include an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion, wherein the strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof.
  • the vane strut may additionally and/or alternatively include an aft mount portion as described above removably attached to the strut mount.
  • a method includes assembling a flap mount assembly, placing a flap mount assembly proximate to a strut mount of a strut, and disposing an aft mount portion around the flap mount assembly such that the aft mount portion and the strut mount form a strut cylinder with threading on an outer diameter thereof.
  • the assembling the flap mount assembly may additionally and/or alternatively include disposing a bushing around a flap post of a flap such that the flap post is attached to the bushing but rotatable relative to the bushing.
  • the method may additionally and/or alternatively include disposing a washer between a portion of the bushing and a portion of the flap.
  • the method may additionally and/or alternatively include securing the flap mount assembly to the strut cylinder by threading a flap spanner nut around the bushing and tightening the flap spanner nut into a flange of the strut cylinder.
  • the method may additionally and/or alternatively include placing the strut cylinder within a turbomachine housing.
  • the method may additionally and/or alternatively include securing the strut cylinder to the turbomachine housing by threading a strut spanner nut around the strut cylinder and tightening the strut spanner nut into the turbomachine housing.
  • the flap mount assembly may additionally and/or alternatively be secured to the strut cylinder before the strut cylinder is secured to the turbomachine housing.
  • the method may additionally and/or alternatively include positioning the flap relative to the vane strut before securing the flap mount assembly to the strut cylinder.
  • FIG. 2 an illustrative view of an embodiment of a system in accordance with the disclosure is shown in Fig. 2 and is designated generally by reference character 200.
  • FIGs. 1 , 3 , and 4 Other embodiments and/or aspects of this disclosure are shown in Figs. 1 , 3 , and 4 .
  • the systems and methods described herein can be used to mount a strut-flap vane to a turbomachine housing.
  • Fig. 1 schematically illustrates an embodiment of a gas turbine engine 20.
  • the gas turbine engine 20 is disclosed herein as a two-spool low-bypass augmented turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26, a turbine section 28, an augmenter section 30, an exhaust duct section 32, and a nozzle system 34 along a central longitudinal engine axis A.
  • augmented low bypass turbofan depicted as an augmented low bypass turbofan in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are applicable to other gas turbine engines including non-augmented engines, geared architecture engines, direct drive turbofans, turbojet, turboshaft, multi-stream variable cycle adaptive engines and other engine architectures.
  • Variable cycle gas turbine engines power aircraft over a range of operating conditions and essentially alter a bypass ratio during flight to achieve countervailing objectives such as high specific thrust for high-energy maneuvers yet optimize fuel efficiency for cruise and loiter operational modes.
  • An engine case structure 36 defines a generally annular secondary airflow path 40 around a core airflow path 42. It should be appreciated that various components, individually and collectively, may define the engine case structure 36 that essentially defines an exoskeleton to support the rotational hardware.
  • Air that enters the fan section 22 is divided between a core airflow through the core airflow path 42 and a secondary airflow through a secondary airflow path 40.
  • the core airflow passes through the compressor section 24, combustor section 26, the turbine section 28, then the augmenter section 30 where fuel may be selectively injected and burned to generate additional thrust through the nozzle system 34.
  • additional airflow streams such as third stream airflow typical of variable cycle engine architectures may additionally be sourced from the fan section 22.
  • the secondary airflow may be utilized for a multiple of purposes to include, for example, cooling and pressurization.
  • the secondary airflow as defined herein may be any airflow different from the core airflow.
  • the secondary airflow may ultimately be at least partially injected into the core airflow path 42 adjacent to the exhaust duct section 32 and the nozzle system 34.
  • the exhaust duct section 32 may be circular in cross-section as typical of an axisymmetric augmented low bypass turbofan or may be non-axisymmetric in cross-section to include, but not be limited to, a serpentine shape to block direct view to the turbine section 28.
  • the exhaust duct section 32 may terminate in a Convergent/Divergent (C/D) nozzle system, a non-axisymmetric two-dimensional (2D) C/D vectorable nozzle system, a flattened slot nozzle of high aspect ratio or other nozzle arrangement.
  • C/D Convergent/Divergent
  • 2D non-axisymmetric two-dimensional
  • a strut-flap vane system 200 for a turbomachine includes a vane strut 211 comprising an airfoil portion 211b and a strut mount 211a extending in a radially outward direction from the airfoil portion 211b.
  • the strut mount 211a forms a hollow semi-cylinder and includes threading 211c on an outer diameter thereof.
  • the system 200 also includes at least one aft mount portion 201 defining a hollow semi-cylinder configured to form a strut cylinder 203 with the strut mount 211a such that the aft mount portion 201 can be disposed in contact with the strut mount 211a to form the strut cylinder 203.
  • the strut cylinder 203 defines a cylinder opening 205.
  • the aft mount portion 201 includes threading 201c on an outer diameter thereof that aligns with the threading 211c of the strut mount 211a to allow a strut spanner nut 207 to mesh with both the strut mount 211a and the aft mount portion 201.
  • a flap mount assembly 209 can be disposed within the cylinder opening and can have a flap post 213a extending from a flap 213 and can be rotatable relative to the strut cylinder 203 to allow the flap 213 to change position relative to the vane strut 211.
  • the flap post 213a can be operatively connected to an actuator servo to rotate the position of the flap 213. This can allow for the camber of the vane to be modified during operation to enhance performance of the engine in different operational conditions.
  • the flap mount assembly 209 can include a bushing 215 disposed around the flap post 213a.
  • the bushing 215 can be disposed on the flap post 213a such that bushing 215 is retained along the length of the flap post 213a but the flap post 213a can rotate relative to the bushing 215 (e.g., via one or more complementary ridges on the inner diameter of the bushing and the outer diameter of the flap post 213).
  • the bushing 215 can include threading 215c on an outer diameter thereof.
  • the bushing 215 can include a bushing flange 215a disposed radially inward of the strut cylinder 203. As shown, a suitable washer 221 can be disposed between the bushing flange 215a.
  • the system 200 can further include a flap spanner nut 217 having threading 217c meshed with the threading 215c on the bushing 215 to secure the bushing 215 and the flap 213 in a position relative to the strut 211 while allowing the flap post 213a to rotate.
  • the flap spanner nut 217 can include crown notches 217a configured to allow a mating tool to torque the flap spanner nut 217 about the bushing 217.
  • the flap spanner nut 217 can be sized to fit at least partially within the cylinder opening 205 and engage with a cylinder flange 203a extending from the strut cylinder. It is contemplated that the flap spanner nut 217 can be sized to the same diameter as or greater diameter than the strut cylinder 203 and can contact the upper surfaces of the strut cylinder 203.
  • the flap spanner nut 217 can include anti-rotation serrations 217b on a surface thereof that contacts the cylinder flange 203a to prevent rotation of the spanner nut 217 after compressing against the cylinder flange 203a.
  • Any other suitable anti-rotation mechanism is contemplated herein (e.g., adhesive).
  • the system 200 can also include a strut spanner nut 207 configured to mount the strut-flap vane 400 to a turbomachine housing 219.
  • the strut spanner nut includes threading 207c that meshes with threading 211c and 201c of the strut mount 211a and the aft mounting portion 201 to retain both to form the strut cylinder 203.
  • the strut spanner nut 207 can include anti-rotation serrations (and/or any other suitable anti-rotation mechanism) on a surface thereof that contacts the turbomachine housing 219. Also, the strut spanner nut 207 can include crown notches 207a configured to allow a mating tool to torque the strut spanner nut 207 about the strut cylinder 203.
  • a method includes assembling a flap mount assembly 209, placing a flap mount assembly 209 proximate to a strut mount 211a of a strut 211, and disposing an aft mount portion 201 around the flap mount assembly 209 such that the aft mount portion 201 and the strut mount 211a form a strut cylinder 203 with threading 211c, 201c on an outer diameter thereof.
  • Assembling the flap mount assembly 209 can include disposing a bushing 215 around a flap post 213a of a flap 213 such that the flap post 213a is attached to the bushing 215 but is also rotatable relative to the bushing 215.
  • the method can further include disposing a washer 221 between a portion of the bushing 215 and a portion of the flap 213.
  • the method can further include securing the flap mount assembly 209 to the strut cylinder 203 by threading a flap spanner nut 217 around the bushing 215 and tightening the flap spanner nut 217 into a flange 203a of the strut cylinder 203.
  • the method can further include placing the strut cylinder 203 within a turbomachine housing 219.
  • the method can further include securing the strut cylinder 203 to the turbomachine housing 219 by threading a strut spanner nut 207 around the strut cylinder 203 and tightening the strut spanner nut 207 into the turbomachine housing 219.
  • the flap mount assembly 209 can be secured to the strut cylinder 203 before the strut cylinder 203 is secured to the turbomachine housing 219 (e.g., at a work bench before installation into the turbomachine).
  • the method can further include positioning the flap 213 relative to the vane strut 211 before securing the flap mount assembly 209 to the strut cylinder 203 (e.g., to reduce a gap between the vane 211 and the flap 213).
  • Embodiments as disclosed herein allow typical manufacturing tolerances to be utilized while providing the flexibility to tightly position the flap 213 relative to the strut 211 (e.g., at the bench before installation into the turbomachine).
  • improved sealing can be realized at all conditions with standard tolerances whereas traditional systems required custom fabrication per strut-flap segment to achieve sealing through tight clearances.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Claims (15)

  1. Entretoise d'aube (211) pour une aube à clapet d'entretoise, comprenant :
    une partie de surface portante (211b) ; et
    un support d'entretoise (211a) s'étendant dans un sens radialement vers l'extérieur depuis la partie de surface portante ;
    caractérisé en ce que le support d'entretoise forme un semi-cylindre creux et comprend un filetage (211c) sur un diamètre extérieur de celui-ci.
  2. Système d'aube à clapet d'entretoise pour une turbomachine, comprenant :
    une entretoise d'aube (211) selon la revendication 1 ; et
    une ou des parties de support arrière (201) définissant un semi-cylindre creux configuré pour former un cylindre d'entretoise (203) avec le support d'entretoise de sorte que la partie de support arrière peut être disposée en contact avec le support d'entretoise pour former le cylindre d'entretoise, dans lequel le cylindre d'entretoise définit une ouverture de cylindre (205), dans lequel la partie de support arrière comprend un filetage (201c) sur un diamètre extérieur de celle-ci qui s'aligne avec le filetage du support d'entretoise pour permettre à un écrou cylindrique d'entretoise (207) de s'engrener avec le support d'entretoise et la partie de support arrière.
  3. Système selon la revendication 2, comprenant en outre un ensemble de support de clapet (209) disposé dans l'ouverture de cylindre, l'ensemble de support de clapet comprenant un montant de clapet (213a) s'étendant depuis un clapet (213) et pouvant être pivoté par rapport au cylindre d'entretoise pour permettre au clapet de changer de position par rapport à l'aube.
  4. Système selon la revendication 3, dans lequel l'ensemble de support de clapet comprend une douille (215) disposée autour du montant de clapet, la douille comprenant un filetage (215c) sur un diamètre extérieur de celle-ci.
  5. Système selon la revendication 4, dans lequel la douille comprend une bride de douille (215a) disposée radialement vers l'intérieur du cylindre d'entretoise.
  6. Système selon la revendication 4 ou 5, comprenant en outre un écrou cylindrique de clapet (217) engrené avec le filetage sur la douille pour fixer la douille et le clapet dans une position relative à l'entretoise tout en permettant au montant de clapet de pivoter.
  7. Système selon la revendication 6, dans lequel l'écrou cylindrique de clapet est dimensionné pour s'adapter au moins partiellement à l'intérieur de l'ouverture de cylindre et s'engager avec une bride de cylindre (203a) s'étendant depuis le cylindre d'entretoise ; de préférence
    dans lequel l'écrou cylindrique de clapet comprend des dentelures anti-rotation sur une surface de celui-ci qui est en contact avec la bride de cylindre pour empêcher la rotation de l'écrou cylindrique après compression contre la bride de cylindre.
  8. Système selon l'une quelconque des revendications 2 à 7, dans lequel l'écrou cylindrique d'entretoise est configuré pour monter l'aube à clapet d'entretoise sur un boîtier de turbomachine (219) ; préférablement
    dans lequel l'écrou cylindrique d'entretoise comprend des dentelures anti-rotation sur une surface de celui-ci qui sont en contact avec le boîtier de turbomachine.
  9. Entretoise d'aube selon la revendication 1, comprenant en outre une partie de support arrière (201) fixée de manière amovible au support d'entretoise et définissant un semi-cylindre creux configuré pour former un cylindre d'entretoise (203) avec le support d'entretoise de sorte que la partie de support arrière peut être disposée en contact avec le support d'entretoise pour former le cylindre d'entretoise, dans lequel le cylindre d'entretoise définit une ouverture de cylindre (205), dans lequel la partie de support arrière comprend un filetage (201c) sur un diamètre extérieur de celle-ci qui s'aligne avec le filetage du support d'entretoise pour permettre à un écrou cylindrique d'entretoise (207) de s'engrener avec le support d'entretoise et la partie de support arrière.
  10. Procédé, comprenant :
    l'assemblage d'un ensemble de support de clapet (209) ;
    le positionnement de l'ensemble de support de clapet à proximité d'un support d'entretoise (211a) d'une entretoise d'aube (211), dans lequel le support d'entretoise s'étend dans un sens radialement vers l'extérieur d'une partie de surface portante (211b) de l'entretoise d'aube, et dans lequel le support d'entretoise forme un semi-cylindre creux ; et
    la disposition d'une partie de support arrière (201) autour de l'ensemble de support de clapet de sorte que la partie de support arrière et le support d'entretoise forment un cylindre d'entretoise (203) avec un filetage (211c, 201c) sur un diamètre extérieur de ceux-ci.
  11. Procédé selon la revendication 10, dans lequel l'assemblage de l'ensemble de support de clapet comprend la disposition d'une douille (215) autour d'un montant de clapet (213a) d'un clapet (213) de sorte que le montant de clapet est fixé à la douille mais est orientable par rapport à la douille ;
    et préférablement le procédé comprenant en outre la disposition d'une rondelle (221) entre une partie de la douille et une partie du clapet.
  12. Procédé selon les revendications 10 ou 11, comprenant la fixation de l'ensemble de support de clapet au cylindre d'entretoise via le filetage d'un écrou cylindrique de clapet (217) autour de la douille et le serrage de l'écrou cylindrique de clapet dans une bride (203a) du cylindre d'entretoise.
  13. Procédé selon l'une quelconque des revendications 10, 11 ou 12, comprenant en outre le placement du cylindre d'entretoise dans un boîtier de turbomachine (219) ; de préférence le procédé comprenant la fixation du cylindre d'entretoise au boîtier de turbomachine par le filetage d'un écrou cylindrique d'entretoise (207) autour du cylindre d'entretoise et le serrage de l'écrou cylindrique d'entretoise dans le boîtier de turbomachine.
  14. Procédé selon la revendication 13 lorsqu'il dépend de la revendication 12, dans lequel l'ensemble de support de clapet est fixé au cylindre d'entretoise avant que le cylindre d'entretoise ne soit fixé au boîtier de turbomachine.
  15. Procédé selon la revendication 14, comprenant en outre le positionnement du clapet par rapport à une entretoise d'aube avant la fixation de l'ensemble de support de clapet au cylindre d'entretoise.
EP16160455.8A 2015-05-15 2016-03-15 Positionnement d'entretoise d'aube et systèmes de fixation Active EP3093442B1 (fr)

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US14/712,999 US9879560B2 (en) 2015-05-15 2015-05-15 Vane strut positioning and securing systems

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EP3093442A1 EP3093442A1 (fr) 2016-11-16
EP3093442B1 true EP3093442B1 (fr) 2018-10-10

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US10502077B2 (en) * 2016-03-17 2019-12-10 United Technologies Corporation Vane retainer
US10781707B2 (en) * 2018-09-14 2020-09-22 United Technologies Corporation Integral half vane, ringcase, and id shroud
US10794200B2 (en) 2018-09-14 2020-10-06 United Technologies Corporation Integral half vane, ringcase, and id shroud

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US3788763A (en) * 1972-11-01 1974-01-29 Gen Motors Corp Variable vanes
US3990810A (en) 1975-12-23 1976-11-09 Westinghouse Electric Corporation Vane assembly for close coupling the compressor turbine and a single stage power turbine of a two-shaped gas turbine
FR2685033B1 (fr) * 1991-12-11 1994-02-11 Snecma Stator dirigeant l'entree de l'air a l'interieur d'une turbomachine et procede de montage d'une aube de ce stator.
US6619916B1 (en) 2002-02-28 2003-09-16 General Electric Company Methods and apparatus for varying gas turbine engine inlet air flow
FR2908828B1 (fr) 2006-11-16 2013-11-01 Snecma Dispositif d'etancheite de volet mobile de roue directrice d'entree d'une turbomachine
US9404374B2 (en) * 2008-04-09 2016-08-02 United Technologies Corporation Trunnion hole repair utilizing interference fit inserts
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US20160333726A1 (en) 2016-11-17
EP3093442A1 (fr) 2016-11-16
US9879560B2 (en) 2018-01-30

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